Fuel jettisoning system.

CFR · 2024-01-01 · US · Title 14

(a) A fuel jettisoning system must be installed on each airplane unless it is shown that the airplane meets the climb requirements of §§ 25.119 and 25.121(d) at maximum takeoff weight, less the actual or computed weight of fuel necessary for a 15-minute flight comprised of a takeoff, go-around, and landing at the airport of departure with the airplane configuration, speed, power, and thrust the same as that used in meeting the applicable takeoff, approach, and landing climb performance requirements of this part. (b) If a fuel jettisoning system is required it must be capable of jettisoning enough fuel within 15 minutes, starting with the weight given in paragraph (a) of this section, to enable the airplane to meet the climb requirements of §§ 25.119 and 25.121(d), assuming that the fuel is jettisoned under the conditions, except weight, found least favorable during the flight tests prescribed in paragraph (c) of this section. (c) Fuel jettisoning must be demonstrated beginning at maximum takeoff weight with flaps and landing gear up and in— (1) A power-off glide at 1.3 V (2) A climb at the one-engine inoperative best rate-of-climb speed, with the critical engine inoperative and the remaining engines at maximum continuous power; and (3) Level flight at 1.3 V (d) During the flight tests prescribed in paragraph (c) of this section, it must be shown that— (1) The fuel jettisoning system and its operation are free from fire hazard; (2) The fuel discharges clear of any part of the

official document · source cfr-2024 · id 14:§ 25.1001